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US 4,734,010 AGranted
Damping element for independent turbomachine blades
AssigneeBBC Brown, Boveri & Company, Limited
InventorJosef Battig
Life of this patent
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Abstract
The present invention relates to a damping element for independent blades of a turbomachine in which the blades fastened in the rotor are connected together, preferably in the radially outer region, the connection between two blades consists of an elastically deformable platelet curved towards the center of the rotor, which platelet engages in retention features on the suction side of one blade and on the pressure side of a second, neighboring blade. The retention features on the blades can be either recesses or protruding lugs, in or on which the platelets are supported.
Claims5
A turbomachine, comprising:
- a plurality of free-standing blades mounted in a rotor, each of said blades having a semicircular recess on the suction side of the blade and a semicircular recess on the pressure side of the blade;
- an elastically deformable platelet having a longitudinal axis and a semicircular support at each longitudinal end;
- the semicircular supports of said platelet being supported in the semicircular recesses of adjacent blades such that the supports are located in a plane extending substantially perpendicularly to the longitudinal extent of the blades and the longitudinal axis of said platelet extends at an angle to the circumferential direction of the rotor;
- and
- said platelet having a double curvature such that when said platelet is mounted between adjacent blades, said platelet curves toward the center of the rotor.
2 more elements
Dependencies are inferred from the claim text.